This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. 

# Proposed Rules Federal Register 

### 8155

Vol. 81, No. 32

Thursday, February 18, 2016

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–0466; Directorate Identifier 2014–NM–188–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A300 B4–603, B4–605R, and B4–622R airplanes; and Model A310–304, –324, and –325 airplanes. This proposed AD was prompted by a report of a crack found on door frame (FR) 73A between stringers 24 and 25. This proposed AD would require inspections around the rivet heads of the seal retainer run-out holes at certain frames and corrective actions if necessary. We are proposing this AD to detect and correct cracking of the door frame, which could result in reduced structural integrity of the airplane.

**DATES :**  We must receive comments on this proposed AD by April 4, 2016.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com . You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 0466; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2016–0466; Directorate Identifier 2014–NM–188–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014– 0202R1, dated September 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 B4–603, B4–605R, and B4–622R airplanes; and Model A310–304, –324, and –325 airplanes The MCAI states:

During the preparation phase for conversion of an A300–600 aeroplane from passenger to freighter configuration, a crack was detected on door frame (FR) 73A, between stringer (STRG) 24 and STRG 25.

DGAC France had issued AD 1999–013– 276R1 [http://ad.easa.europa.eu/ad/F-1999- 013-276R1 ] to require inspections at FR 73A in accordance with the instructions of Airbus Service Bulletin (SB) A310–53–2107 or SB A300–53–6116, as applicable. However, the new crack was found in an area not covered by the existing inspection and is therefore addressed by this new [EASA] AD. (DGAC France AD 1999–013–276R1 remains in place).

Further investigations identified that, on A300–600 aeroplanes, the areas at FR 56A and FR 57A have the same design and material as at FR 73A.

This condition, if not detected and corrected, could affect the structural integrity of the airframe.

For the reasons described above, this [EASA] AD requires repetitive [high frequency eddy current (HFEC)] inspections of the rivet heads of the seal retainer run out holes to detect cracks and, depending on findings, accomplishment of corrective actions [repair].

Even though no crack has been identified at FR 56A and FR 57A, as a preventive measure, the inspection is extended to these areas. On A310 aeroplanes, only the area at FR 73A needs to be inspected.

This [EASA] AD is revised to reduce the applicability to aeroplanes in post-MOD 06924 configuration.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–
0466.

Related Service Information Under 1 CFR Part 51

Airbus has issued Service Bulletins A300–53–6175, and A310–53–2138, both dated May 28, 2014. The service


### 8156 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules

information describes procedures to do HFEC inspections around the rivet heads of the seal retainer run-out holesat certain frame locations on the lefthand and right-hand sides. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section. FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance

We estimate that this proposed AD affects 24 airplanes of U.S. registry.

We also estimate that it would take about 11 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $22,440, or $935 per product.

We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation:

1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

3. Will not affect intrastate aviation in Alaska; and

4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA–2016–0466; Directorate Identifier 2014–NM–188–AD.

(a) Comments Due Date

We must receive comments by April 4,
2016.
(b) Affected ADs

None. (c) Applicability

This AD applies to Airbus Model A300B4– 603, A300B4–605R, A300B4–622R, A310– 304, A310–324, and A310–325 airplanes; certificated in any category; all manufacturer serial numbers (MSNs) in post-modification (MOD) 06924 configuration, except MSN 464, 477, 479, 481, 482, 483, 484, and 488.

Note 1 to paragraph (c) of this AD: MSNs 464, 477, 479, 481, 482, 483, 484 and 488 partially embodied MOD 06924 by means of modification proposal D05902. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason

This AD was prompted by a report of a crack found on door frame (FR) 73A between stringers 24 and 25. We are issuing this AD to detect and correct cracking, which could reduce the structural integrity of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Inspection

At the later of the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a high frequency eddy current (HFEC) inspection for any crack around the rivet heads of the seal retainer run-out holes at FR 56A, FR 57A, and FR 73A, left-hand (LH) and right-hand (RH) sides on Model A300–600 airplanes; and at FR 73A, LH and RH sides on Model A310 airplanes; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 53–2138, dated May 28, 2014; or Airbus Service Bulletin A300–53–6175, dated May 28, 2014; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 7,500 flight cycles.

(1) Before the accumulation of 32,000 total flight cycles.

(2) Within 36 months after the effective date of this AD, or before the accumulation of 36,000 total flight cycles, whichever occurs first.
(h) Corrective Actions

If any crack is found during any inspection required by paragraph (g) of this AD, repair before further flight using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA).
(i) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.


### 8157 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(3) Required for Compliance (RC): Except as required by paragraph (h) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.
(j) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014–0202R1, dated September 19, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–0466.

(2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com

. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on February 6, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–03135 Filed 2–17–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–3697; Directorate Identifier 2015–NM–143–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT. **ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede Airworthiness Directive (AD) 2011–01– 15, which applies to certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. AD 2011–01–15 currently requires repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at stringers S–4L (left) and S–4R (right), from stations (STA) 297 through STA 439, and repair, if necessary. AD 2011–01–15 also includes terminating action for the repetitive inspections of the repaired areas only. Since we issued AD 2011–01–15, we received reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. This proposed AD would add repetitive inspections for cracking in additional areas and repair if necessary. This proposed AD would also remove airplanes from the applicability in AD 2011–01–15. This proposed AD would also add an optional skin panel replacement which would terminate all inspections and an optional preventative modification that would terminate certain inspections. We are proposing this AD to detect and correct fatigue cracking of the fuselage skin of the crown skin panel, which could result in pressure venting and consequent rapid decompression of the airplane.

**DATES :**  We must receive comments on this proposed AD by April 4, 2016.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone: 206–544– 5000, extension 2; fax: 206–766–5683; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–
3697. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 3697; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5348; fax: 562–627–5210; email: eric.schrieber@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2016–3697; Directorate Identifier 2015–NM–143–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On December 28, 2010, we issued AD 2011–01–15, Amendment 39–16572 (76 FR 1351, January 10, 2011), for certain The Boeing Company Model 757–200, –200CB, and –300 series airplanes. AD 2011–01–15 requires repetitive inspections for cracking of the fuselage skin of the crown skin panel along the